EP3330177B1 - Steuerorgan, drehflügelflugzeug und verfahren - Google Patents

Steuerorgan, drehflügelflugzeug und verfahren Download PDF

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Publication number
EP3330177B1
EP3330177B1 EP17200291.7A EP17200291A EP3330177B1 EP 3330177 B1 EP3330177 B1 EP 3330177B1 EP 17200291 A EP17200291 A EP 17200291A EP 3330177 B1 EP3330177 B1 EP 3330177B1
Authority
EP
European Patent Office
Prior art keywords
control
aircraft
control member
shaft
thrust
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
EP17200291.7A
Other languages
English (en)
French (fr)
Other versions
EP3330177A1 (de
Inventor
Jean-Romain Bihel
Zouhair SASSI
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Airbus Helicopters SAS
Original Assignee
Airbus Helicopters SAS
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Filing date
Publication date
Application filed by Airbus Helicopters SAS filed Critical Airbus Helicopters SAS
Publication of EP3330177A1 publication Critical patent/EP3330177A1/de
Application granted granted Critical
Publication of EP3330177B1 publication Critical patent/EP3330177B1/de
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/54—Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement
    • B64C27/56—Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement characterised by the control initiating means, e.g. manually actuated
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C13/00—Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers
    • B64C13/02—Initiating means
    • B64C13/04—Initiating means actuated personally
    • B64C13/14—Initiating means actuated personally lockable
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/54—Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement
    • B64C27/58—Transmitting means, e.g. interrelated with initiating means or means acting on blades
    • B64C27/59—Transmitting means, e.g. interrelated with initiating means or means acting on blades mechanical
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/82—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D31/00—Power plant control systems; Arrangement of power plant control systems in aircraft
    • B64D31/02—Initiating means
    • B64D31/04—Initiating means actuated personally
    • G—PHYSICS
    • G05—CONTROLLING; REGULATING
    • G05G—CONTROL DEVICES OR SYSTEMS INSOFAR AS CHARACTERISED BY MECHANICAL FEATURES ONLY
    • G05G1/00—Controlling members, e.g. knobs or handles; Assemblies or arrangements thereof; Indicating position of controlling members
    • G05G1/08—Controlling members for hand actuation by rotary movement, e.g. hand wheels
    • G05G1/10—Details, e.g. of discs, knobs, wheels or handles
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
    • B64C11/30—Blade pitch-changing mechanisms
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C13/00—Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers
    • B64C13/02—Initiating means
    • B64C13/04—Initiating means actuated personally
    • B64C13/042—Initiating means actuated personally operated by hand
    • B64C13/0421—Initiating means actuated personally operated by hand control sticks for primary flight controls
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C13/00—Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers
    • B64C13/02—Initiating means
    • B64C13/04—Initiating means actuated personally
    • B64C13/044—Initiating means actuated personally operated by feet, e.g. pedals
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/82—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft
    • B64C2027/8227—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft comprising more than one rotor

Definitions

  • the present invention relates to a control member, a rotary wing aircraft comprising such a control member, and a method applied by the aircraft.
  • a helicopter type rotary wing aircraft for example comprises at least one main rotor which at least partially participates in the lift and propulsion of this aircraft.
  • a system allows at least to control the yaw movement of the aircraft.
  • a helicopter has three axes of control.
  • a first axis is to use a first command to control the vector of the lift vector of the aircraft.
  • a second axis is to use a second command to control the orientation of this lift vector, and
  • a third axis is to use a third command to control the yaw motion of the aircraft.
  • a helicopter may comprise a main rotor involved in its propulsion and lift.
  • a helicopter may comprise an auxiliary rotor participating at least in the control of the yaw movement.
  • the aircraft includes piloting controls operable by a pilot to control the evolution of this aircraft.
  • a collective lever collectively controls the pitch of the main rotor blades to adjust the lift of the aircraft.
  • a cyclic stick cyclically controls the pitch of the main rotor blades to adjust the orientation of the lift vector of the aircraft.
  • a rudder collectively adjusts the pitch of the auxiliary rotor blades to control the yaw motion of the helicopter.
  • a helicopter may comprise two main rotors, possibly coaxial.
  • a collective lever can collectively control the pitch of the main rotor blades to adjust the lift of the aircraft.
  • a cyclic stick can make it possible to control cyclically the pitch of the blades of the main rotors to adjust the orientation of the lift vector of the aircraft.
  • a rudder can be used to adjust the yaw torque exerted by at least one main rotor on the fuselage of the aircraft, to control the yaw movement of the aircraft.
  • hybrid Another type of rotary wing aircraft called “hybrid” for convenience includes at least one rotor that participates at least partially in the lift and propulsion of this aircraft.
  • the aircraft comprises a device for controlling the yaw movement of the aircraft.
  • This aircraft also comprises a motor system capable of exerting, at least in the direction of advancement of the aircraft, a thrust called “additional thrust” for convenience.
  • This additional thrust is described as “additional” insofar as this thrust is axially independent of the thrust possibly exerted by the rotary wing.
  • such a hydride rotary wing aircraft comprises a fourth steering axis.
  • This fourth control axis consists of using a fourth command to drive the additional thrust standard.
  • a hybrid rotary wing aircraft may comprise a main rotor that participates at least partially the lift and propulsion of this aircraft.
  • this hybrid rotary wing aircraft comprises two engine systems respectively provided with two propellers participating at least partially in the propulsion of the aircraft and in the control of the yaw movement of this aircraft.
  • a collective pitch lever may collectively control the pitch of the main rotor blades to adjust the lift vector standard of the aircraft.
  • a cyclic stick can be used to cyclically control the pitch of the main rotor blades to adjust the orientation of the lift vector of the aircraft.
  • a thrust control may allow a pilot to collectively adjust an average pitch of the propeller blades to control the additional thrust generated jointly by the propellers.
  • a rudder can be used to adjust the distribution of this additional thrust between the two propellers to control the yaw movement of the aircraft through the application of different thrusts using the propellers.
  • This rudder can for example be used to adjust a differential pitch, the pitch of the blades of a helix being for example equal to the sum of the average pitch and the half of the differential pitch, the pitch of the blades of the other helix being for example equal to the difference of the average pitch and the half of the differential pitch.
  • the thrust control can take the form of an electrical control command "all or nothing".
  • this thrust command When the thrust control is maneuvered, this thrust command generates an order of increase or decrease of the average pitch of the propeller blades. This order is transmitted to actuators to change the pitch of the blades of the two propellers in the same way.
  • an actuator is arranged on a mechanical transmission chain controlling a hydraulic distributor, the hydraulic distributor supplying a hydraulic cylinder capable of generating a movement of the blades of a propeller.
  • the document FR 1518834 has a lever control.
  • This lever is mobile. The movement is guided by a guide having an A-shaped guide slot (lambda).
  • the lever carries a rotating handle controlling the fuel intake of a power unit.
  • the document GB 790560 presents an aircraft command.
  • This control comprises a tube movable in rotation about a transverse axis of rotation.
  • the tube is connected to a control rod of the collective pitch of the blades of a rotor. A rotation of the tube then induces a modification of this collective step.
  • this control is provided with a rod passing through the tube.
  • This rod extends longitudinally from a handle projecting towards the front of the tube towards an end projecting towards the rear of the tube.
  • This end is articulated to a mobility system controlling the position of a valve.
  • the handle is rotatable relative to the tube about a longitudinal axis between a first position and a second position.
  • a rotation of the tube about its transverse axis of rotation induces only a modification of the collective pitch of the rotor blades.
  • a rotation of the tube about its transverse axis of rotation induces a change in the collective pitch of the rotor blades and the position of the valve controlled by the handle.
  • the present invention therefore aims to provide an innovative control member operable by a pilot and may in particular be used to control a thrust of an aircraft.
  • the invention thus aims at a control member operable by a pilot, said control member being intended to control a motor system exerting a thrust in an aircraft, the control member comprising a handle and a mobile assembly arranged on the handle and movable relative to this handle, the movable assembly comprising a handle.
  • Such a motor system may for example take the form of a reactor or a propeller.
  • the handle is linked to the handle by a helical connection so that a rotation of the handle around the handle generates a translation of the handle and the moving assembly along the handle, the handle being movable in translation in a first direction of translation for example to impose an increase in thrust, the handle being movable in translation in a second direction of translation opposite to the first direction of translation and for example intended to impose a decrease in said thrust.
  • the thrust is subsequently considered to be positive when this thrust permits advance the aircraft, according to a direction of travel from the tail to the nose of the aircraft, and negative otherwise.
  • increase refers to an increase in thrust. Such an increase can in particular make it possible to reverse the direction of the thrust by transforming a negative thrust into a positive thrust.
  • An increase in the thrust may be to impose an acceleration of the aircraft along the direction of travel.
  • decrease refers to a decrease in thrust. Such a decrease can in particular make it possible to reverse the direction of the thrust by transforming a positive thrust into a negative thrust. A decrease in the thrust may be to impose a deceleration of the aircraft according to the direction of travel.
  • the mobile assembly of the control member has a handle helically connected to the handle.
  • a handle may take the form of a cylinder which locally surrounds a tube of the handle.
  • control member does not comprise a handle that is only mobile in rotation, contrary to the document FR 1518834 for example, or only mobile in translation.
  • the handle performs a rotation-translation movement from the helical link. As the handle is turned around the handle, this handle is moved in translation.
  • a pilot can intuitively move the handle to increase or reduce the thrust exerted by each motor system controlled by the control member.
  • a pilot grasping the handle of one hand can exert a major effort on a mechanical transmission connected to the movable assembly.
  • the total effort exerted by the pilot on the mechanical transmission results from a combination of a force developed in rotation by his hand to turn the handle and a force developed in translation exerted by the driver's arm.
  • Such a combination of effort can not be achieved with a conventional handle, and may be advantageous for moving elements requiring significant control efforts.
  • a helically connected handle can be positioned precisely by a pilot relative to the handle, unlike a handle movable only in translation.
  • control means embodied by the movable assembly of the control member is purely mechanical. Its operation is embodied by the rotary actuation of a handle, which generates a translation action of the mobile assembly comprising the same handle.
  • This mobile assembly is mounted on the handle, for example a handle controlling the collective pitch of a main rotor, and its operation may not influence the control generated by the stick as such.
  • this controller can tend to be robust, ergonomic, practical, and to be used intuitively.
  • This control member can thus be used on a hybrid helicopter to control the thrust exerted collectively by the propellers.
  • the handle may for example allow emergency management of the thrust exerted by the propellers.
  • the rotation of the handle generates, through a helical assembly, a longitudinal movement of the handle on the handle to help the pilot to understand the direction of the variation of thrust (acceleration forward, deceleration backwards) .
  • the rotational movement of the handle may furthermore be indexed to the movement of a needle of a thrust needle indicator of the dashboard.
  • the controller may further include one or more of the following features.
  • control member may comprise a mechanical movement transmission, said mechanical motion transmission comprising at least one movable link mechanically fixed to the moving assembly.
  • mechanical motion transmission designates a mechanical system provided with at least one link that can be moved at least partially linearly.
  • a transmission may for example comprise at least one ball drive having a blade movable in translation, a cable control having a cable movable in translation, a connecting rod ...
  • the mechanical motion transmission then extends from an input portion comprising a link linked to the moving assembly to an output portion.
  • a single link extends from the input portion to the output portion.
  • the translation of the moving assembly following the rotation of the handle generates an identical translation of the input portion and a movement of the output portion.
  • the output portion performs a translation of the same amplitude and / or in the same direction as the input portion and the moving assembly.
  • the movable assembly may comprise a base that cooperates with the handle, the handle being articulated to the base by a pivot connection conferring a degree of freedom in rotation to the handle relative to the base and around the handle, the base being mounted on the handle by a slide connection, the handle being movable in rotation with respect to the base and being secured in translation of the base, the base being movable only in translation relative to the handle.
  • the mechanical transmission of motion is fixed to the base.
  • the moving assembly may be adapted to control a control actuator requiring a displacement of this moving assembly over a control amplitude to cover a whole range of operation of this driving actuator.
  • the moving assembly When not operating, the moving assembly is in a position centered between a first stop and a second stop, the first stop and the second stop being reached by the moving assembly from the centered position following a translational movement of the assembly. mobile according to said control amplitude.
  • the handle can be a backup control system.
  • the handle can be rendered inoperative in certain operating phases, for example outside a case of failure of a main control interface driving the control actuator or outside training phases.
  • This device then makes it possible to ensure that the moving assembly can drive the control actuator over the entire range of operation of this control actuator, regardless of the state of the control actuator when the handle is made operative.
  • the handle is free to rotate over a maximum amplitude of plus or minus 270 degrees which generates a translation of the moving assembly of plus or minus 75 millimeters with respect to the centered position and a predetermined positive direction of movement.
  • a rotation of the handle 270 degrees in a first direction of rotation induces a translation of 75 millimeters in the first direction of translation.
  • a rotation of the handle 270 degrees in a second direction of rotation induces a translation of 75 millimeters in the second direction of translation.
  • the maximum displacement capacity of the moving assembly is then 150 millimeters, which is twice the total useful stroke provided for the control actuator.
  • the thrust force developed by the driver is of the order of 10 daN (decanewton) output handle.
  • the handle may extend longitudinally from a proximal end to a free end, the proximal end being provided with a hinge giving the handle a degree of freedom in rotation about an axis of rotation.
  • the first direction of translation can go from the proximal end to the free end.
  • the first direction is parallel if necessary with the forward direction of the aircraft.
  • the handle may be arranged between said proximal end and said free end, the handle being independent of the handle for a rotation of the handle about its axis of rotation does not induce a movement of the handle along of the handle.
  • the invention also relates to an aircraft.
  • This aircraft is provided with at least one engine system exerting a thrust, the thrust being regulated by at least one control actuator, the control actuator being controlled by a chain of transmission of a movement opening on the control actuator .
  • the aircraft then comprises at least one control member according to the invention, this control member being mechanically connected to the transmission chain of a movement and being intended to move the transmission chain of a movement.
  • the transmission chain of a movement may comprise at least one control actuator, this control actuator being controlled by an avionic control interface requested by a pilot.
  • control interface designates a device activated by a pilot, such as for example a button or the like, a touch screen, a voice command, etc.
  • avionics means that the control interface generates an electrical, electrical, digital, or optical signal to drive a change of state of the actuator, namely the relative displacement of two parts of this actuator.
  • the control member requires the extension or retraction of the actuator in the context of a linear actuator, a rotation of a rod in the context of a rotary actuator, or a deformation within the scope of a piezoelectric actuator.
  • This command interface can be a main system used by default.
  • control member does not require a change of state of the control actuator, but moves this control actuator mechanically.
  • the control member may be a backup means used in the event of failure of the control interface or during training phases.
  • the aircraft may comprise two propeller-driven systems, the thrust exerted by each propeller of a motor system being controlled by modifying a pitch of the blades of this propeller, the aircraft may comprise a control system operable by a pilot for modifying the thrusts exerted by the two propellers in a different manner, the control member making it possible to modify the thrusts exerted by the two propellers in the same way, the transmission chain of a movement comprising at least one combiner connected to the control member and the control system and the two propellers, the combiner mechanically combining a displacement generated by the control member and a displacement generated by the control system.
  • the combiner may be of a known type.
  • teaching the document FR 3027871 is applicable.
  • control member may comprise a mechanical transmission of motion integral in translation of the movable assembly
  • a lever may be articulated on the one hand to the mechanical transmission of movement and on the other hand to the chain of motion. transmission of a movement, said lever being rotatable about a hinge axis.
  • a simple lever serves as an interface between the two subsystems, which is simple to implement.
  • the aircraft may comprise a plurality of control members each comprising a mechanical movement transmission connected to the movable assembly of the associated control member, each mechanical movement transmission being articulated to the lever.
  • a pilot control and a co-pilot command are of the type of the control device according to the invention.
  • the mobile assemblies of the two control members are then connected to the same lever. The combination of orders between these two control devices is thus naturally by this common lever.
  • the hinge axis can extend between two extreme zones of the lever, the mechanical transmission of movement and the transmission chain of a movement can be articulated to the lever between the axis of articulation and the same extremal zone.
  • the lever may not generate a change of direction of a movement.
  • the aircraft may comprise a immobilization system operable by a pilot to immobilize the lever in normal operation, namely for example as long as the control actuator can be controlled without maneuvering the handle of the control member.
  • the lever In normal and therefore nominal operation, the lever is locked in one position. If necessary, the lever serves as an anchor point for an electrically controlled piloting actuator. By cons, the lever is unlocked if necessary to allow control of the control actuator by the movable assembly of a control member according to the invention.
  • the immobilization system may be provided with a mechanical system which comprises a locking finger movable in translation and a lever orifice, the locking finger being engaged in said orifice to prevent rotation of the lever in normal operation and being disengaged from this port to allow a rotation of the lever in manual operation.
  • the finger can be integral in translation with a gripping means to be maneuvered by a pilot.
  • the invention also relates to a method for controlling a motor system of an aircraft according to this invention.
  • the handle is rotated in a first direction of rotation to translate it along the handle in the first direction of translation to increase the thrust exerted by the engine system, and the handle is turned in a second direction of rotation to translate it along the handle in the second direction of translation to reduce the thrust exerted by the engine system.
  • the aircraft may have an indicator having a scale illustrating thrust values and a needle pointing on this scale a value of a current thrust, said needle rotating according to a first direction of displacement when the thrust increases and in a second direction of displacement when the thrust decreases, said first direction of rotation is identical to said first direction of movement, said second direction of rotation is identical to said second direction of displacement.
  • the handle can move longitudinally homogeneously to the given thrust order as indicated above.
  • the handle can move in rotation homogeneously to the displacement of the needle illustrating this thrust on an indicator.
  • a rotation of the handle in a dextral direction can induce a displacement of the needle in the same direction dextrorsum.
  • the figure 1 has a control member 40 according to the invention in three dimensions, and the figure 2 represents kinematically the control member 40.
  • This control member 40 is intended to control a driving system 10 exerting a thrust, for example in an aircraft 1.
  • the control member 40 has a handle 41.
  • This handle 41 extends from an end called “proximal end 42" to an end called “free end 43".
  • the proximal end 42 can be hinged to a floor by a hinge 70.
  • This hinge 70 can give the handle 41 a degree of freedom in rotation only about an axis of rotation AX2.
  • the handle 41 may represent a collective lever, the rotation of the control sleeve according to known methods a modification of a collective pitch of a rotor blades.
  • a collective pitch lever is hereinafter referred to as a "collective joystick” so as not to be confused with an interface lever according to the invention.
  • the free end 43 may carry various control buttons.
  • this free end 43 may carry an avionic control interface 18 controlling said thrust under normal conditions.
  • control member has an additional mechanical control arranged on the handle.
  • This control takes the form of a mobile assembly 50 which is arranged on the handle 41 and movable in translation along the handle 41.
  • the moving assembly 50 comprises a handle 55.
  • a handle 55 may take the form of a cylinder surrounding the handle.
  • This handle 55 is linked to the handle 41 by a helical connection 57.
  • Such a helical connection 57 may comprise at least two guide members including a helical rail 58 having a predetermined screw pitch and a pin 59 sliding in the helical rail 58.
  • One of said two guide members is then integral with the handle 41 and the other guide member is integral with the handle 55.
  • a helical rail 58 is hollowed in a surface of the handle 41 and a pin 59 protrudes from an inner surface of the handle 55 to be arranged in the rail.
  • a helical rail 58 is dug in an inner surface of the handle, and a pin 59 protrudes from the surface of the handle to be arranged in the helical rail of the handle.
  • a rotation of the handle 55 about an axis of extension of the handle 41 generates a translation of the handle 55 and the moving assembly 50 along the extension axis.
  • Such an axis of extension may represent an axis of symmetry of the portion of the handle along which the moving assembly moves.
  • the handle 55 is independent of the handle 41.
  • a rotation of the handle about its axis of rotation AX2 does not induce a movement of the handle 55 and the movable assembly 50 relative to the handle 41.
  • control member 40 presented comprises a mechanical transmission of movement 36.
  • This mechanical transmission of movement 36 is mechanically fixed to the moving assembly 50 for transferring an order given by the moving assembly through a displacement.
  • the mobile assembly 50 may comprise a base 60 which cooperates with the handle 55.
  • the handle 55 is then connected to the base 60 by a pivot connection 62 which confers a degree of freedom in rotation to the handle 55 relative to the base 60.
  • the base takes the form of a housing 61 in which is disposed one end of the handle. This end can only rotate around the axis of extension relative to the housing 61, the operating clearances.
  • the base 60 is fixed to the handle 41 by a slide link 65.
  • the slide link 65 may comprise two guide means including an elongated rail 66 and a pin 67 sliding in the elongate rail 66, one of the two guide means being integral with the handle 41 and the other guide member being integral with the base 60.
  • an elongated rail 66 is hollowed in the handle 41 and a pin 67 is fixed to the base 60 to slide in the elongated rail 66.
  • the rail Longiline 66 may be disposed following the helical rail 58 where appropriate.
  • the handle 55 is rotatable relative to the base 60.
  • the handle 55 and the base 60 are integral in translation along the handle 41.
  • a link of the mechanical transmission of movement 36 is advantageously fixed to the base 60, not to undergo the rotational movement of the handle 55 and move only in translation.
  • a rotation of the handle 55 according to a first direction of rotation 103 can induce a displacement in translation of the moving assembly 50 in a first translational direction 101, for example to require an increase in the thrust exerted by the controlled drive systems.
  • a rotation of the handle 55 in a second direction of rotation 104 opposite to the first direction of rotation 103 can induce a displacement in translation of the moving assembly 50 in a second direction of translation 102 opposite the first direction of translation , for example to require a decrease in said thrust.
  • the first translational direction 101 may be directed substantially in the direction of advance AV of an aircraft and the proximal end 42 towards the free end 43.
  • substantially in the direction of advance AV means that the direction of translation is parallel to a vertical plane passing through the direction of travel, and perpendicular to the pitch axis of the aircraft for example.
  • the first direction of rotation and the second direction of rotation may be homogeneous with the operation of an indicator 80.
  • the aircraft may comprise an indicator 80 which has a scale 81 illustrating thrust values.
  • the indicator 80 has a rotating needle 83 which points on this scale a value of a current thrust, namely the thrust developed by the motor systems.
  • This needle 83 rotates in a first direction of movement 105 when the thrust increases, and in a second direction of movement 106 when the thrust decreases.
  • the second direction of movement 106 is opposed to the first direction of movement 105.
  • a pilot can rotate the handle 55 in the first direction of rotation 103 to translate it along the handle 41 in the first direction of translation 101 in order to increase the thrust exerted by the motor systems 10 controlled, and rotates the handle 55 in the second direction of rotation 104 to translate it along the handle in the second direction of translation 102 to reduce the thrust exerted by the controlled motor systems 10.
  • first direction of rotation 103 may be identical to the first direction of displacement 105
  • second direction of rotation 104 is identical to the second direction of displacement 106.
  • the maneuver of the mobile unit is thus highly intuitive.
  • the moving assembly can be moved between two extreme positions, and for example between a first stop 201 and a second stop 202.
  • said movable assembly 50 When the moving assembly is rendered inoperative for example, said movable assembly 50 may be in a position called "centered POS0 position" not visible on the figure 1 . In this centered position, the moving assembly 50 is equidistant from the first stop 201 and the second stop 202.
  • this mobile assembly 50 is intended to control at least one control actuator 14 requiring a displacement of the moving assembly 50 over a predetermined control amplitude to cover the entire operating range of this control actuator 14, said distance is equal to said control amplitude. From the centered POS0 position, the first stop 201 or the second stop 202 are reached by the moving assembly 50 following a translational movement of the moving assembly according to said control amplitude.
  • the figure 4 presents an aircraft 1 according to the invention.
  • This aircraft 1 is provided with at least one control member 40 for controlling at least one engine system 10.
  • This engine system exerts a thrust for moving the aircraft 1.
  • This aircraft 1 comprises a fuselage 2 which extends longitudinally in a direction of advance AV of the aircraft from a tail 3 to a nose 4.
  • the aircraft 1 may be a rotorcraft. Therefore, the aircraft can comprise at least one rotor 3 which at least partially participates in the lift of the aircraft or even its propulsion. Such a rotor 3 can be carried by the fuselage 2. This rotor comprises a plurality of blades with variable pitch.
  • this aircraft also comprises at least one engine system capable of exerting a thrust, at least in the direction of advance of the aircraft.
  • the aircraft 1 comprises two engine systems 10 provided respectively with two propellers 11, 12.
  • the two propellers 11, 12 can be arranged transversely on either side of the fuselage and carried by a wing 7.
  • Each propeller 11, 12 comprises a plurality of blades 13 with variable pitch.
  • the propellers 11, 12 and the rotor 3 can be set in motion by a conventional power plant.
  • a power plant may include at least one motor and various power transmission boxes for example.
  • the aircraft comprises a cyclic control maneuverable by a pilot to cyclically control the pitch of the blades of the rotor in the usual manner.
  • the cyclic control may take the form of a conventional cyclic stick for example.
  • the aircraft comprises a collective command 7 operable by a pilot to collectively control in a usual manner the pitch of the rotor blades 3.
  • the collective control can take the form of a joystick collective pitch for example.
  • the collective control and the control member 40 can form one and the same equipment.
  • an avionic control interface may allow a pilot to collectively adjust the thrust exerted by the propellers, for example by adjusting a mean pitch of the propeller blades.
  • a control system 16 possibly a rudder, can for example be used to adjust a differential pitch, the pitch of the blades of a helix being for example equal to the sum of the average pitch and the half of the differential pitch, the not blades of the other helix being for example equal to the difference of the average pitch and the half of the differential pitch.
  • control member 40 can then represent a backup system for controlling the average pitch in the event of failures of the avionic control interface 18 or during driving training for example.
  • the collective control 7 can then include the handle 41 of the control member 40.
  • the avionic control interface can be carried by the handle 41.
  • control member 40 according to the invention can also be arranged on other types of aircraft, for example to control the thrust of a reactor.
  • the figure 5 schematically illustrates a pilot architecture on an aircraft of the type of the figure 4 .
  • the pitch of the blades 13 of each propeller can be modified.
  • the aircraft comprises for each propeller an actuator referred to as a "control actuator 14" which modifies the pitch of the associated blades on command.
  • control actuators 14 are controlled by a conventional control chain called "motion transmission chain 20" for convenience. This chain of transmission of a movement can be controlled by the control system 16 and the control interface 18.
  • This control interface 18 may be an avionic control generating a signal transmitted to at least one actuator 17 of the chain of transmission of a movement.
  • Such an actuator is referred to as a "steering actuator" for convenience.
  • the driving actuators and the rudder are mechanically connected to a combiner 22, this combiner 22 being connected to each control actuator 14.
  • This combiner 22 may take the form of a conventional combiner.
  • this architecture has a mechanical backup system that can be used, particularly in the event of a failure of the control interface 18.
  • This emergency system includes at least one control member 40 according to the invention.
  • the figure 5 illustrates the presence possible a control member 40 operable by a pilot and a control member 40 operable by a co-pilot.
  • Each control member 40 comprises a mobile assembly 50 which is movable in translation and mechanically connected by a mechanical transmission of movement 36 to a single lever 31.
  • This lever 31 is thus articulated on the one hand to each mechanical transmission of movement 36 and the other hand to the chain of transmission of a movement 20.
  • lever cooperates with an immobilization system 37 which renders the lever 31 inoperative on request.
  • the lever When the lever is inoperative under normal operating conditions, the lever serves as anchor point of the control actuators 17. A change of state of the control actuators 17 in fact induces a movement of the combiner.
  • the control member does not control the control actuators.
  • the mobile assemblies of each control member are immobile in their reference systems.
  • the figure 6 presents the various organs of the architecture of the figure 2 .
  • each movable assembly 50 of the control members 40 is connected to a common lever 31 by a mechanical movement transmission 36.
  • a mechanical transmission may comprise a sheath 361 bearing against a support 362.
  • the mechanical transmission of movement 36 may comprise a cable or a blade passing through the sheath to be fixed (e) to the movable assembly 50 and the lever 31.
  • the lever 31 is articulated to a stationary member of the aircraft by a hinge which gives the lever 31 a degree of freedom in rotation about an axis of articulation AX1.
  • the lever extending along the length between two end zones 32, 33, the hinge axis AX1 is positioned between these end zones 32, 33.
  • each mechanical transmission of movement 36 is optionally articulated to the lever 31 between the hinge axis AX1 and a particular end zone.
  • an immobilization system 37 possible makes it possible to immobilize on request the lever 31.
  • This immobilization system 37 may comprise a rod whose end represents a locking pin 38.
  • This locking pin 38 can be inserted into a port 39 of the lever 31 to prevent rotation of the lever 31 about its axis of articulation AX1.
  • the rod may also comprise a gripping means 380. Therefore, a pilot can seize the gripping means 380 to release the locking finger from the orifice 39 in order to release the lever 31.
  • the transmission chain of a movement 20 is articulated to the lever 31 between this hinge axis AX1 and the same particular end zone.
  • this lever thus serves as an anchor point of the transmission chain of a movement.
  • this transmission chain of a movement 20 comprises at least one control actuator 17 controlled by a control interface 18 or by an automatic control system.
  • this transmission chain of a movement 20 may comprise connecting rods, return means, a combiner 22 ...
  • This combiner 22 may be connected by ball drives, or even by connecting rods to the control actuators 14.
  • the transmission chain of a movement 20 is shown schematically.
  • control actuators 17 are controlled to change state and transmit a moving order by a mechanical control connected to each control actuator 14.
  • the lever 31 then isolates the chain of transmission of a movement of control members 40.
  • a displacement of a moving assembly 50 induces a displacement of at least one link of a mechanical transmission of movement 36, a rotation of the lever 31, and then a displacement of members of the transmission chain of a movement 20, and finally an input of the control actuators 14.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Automation & Control Theory (AREA)
  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Mechanical Control Devices (AREA)
  • Transmission Devices (AREA)

Claims (16)

  1. Von einem Piloten betätigbares Steuerorgan (40), wobei das Steuerorgan (40) vorgesehen ist, um ein Antriebssystem (10) zu steuern, das in einem Luftfahrzeug (1) einen Schub ausübt, wobei das Steuerorgan (40) einen Stiel (41) und eine bewegliche Anordnung (50) umfasst, die bewegliche Anordnung (50) auf dem Stiel (41) angeordnet ist und in Bezug auf diesen Stiel (41) beweglich ist, und die bewegliche Anordnung (50) einen Griff (55) umfasst,
    dadurch gekennzeichnet, dass der Griff (55) mit dem Stiel (41) durch eine Schraubenverbindung (57) verbunden ist, so dass eine Drehung des Griffs (55) um den Stiel (41) eine Translation des Griffs (55) und der beweglichen Anordnung (50) entlang des Stiels (41) bewirkt, der Griff (55) in einer besagten Translation in einer ersten Translationsrichtung (101) beweglich ist, und der Griff (55) in einer besagten Translation in einer zweiten Translationsrichtung (102) entgegengesetzt zu der ersten Translationsrichtung (101) beweglich ist.
  2. Steuerorgan nach Anspruch 1,
    dadurch gekennzeichnet, dass das Steuerorgan (40) eine mechanische Bewegungsübertragung (36) aufweist, wobei die mechanische Bewegungsübertragung mindestens eine bewegliche Verbindung umfasst, die mechanisch an der beweglichen Anordnung (50) befestigt ist.
  3. Steuerorgan nach Anspruch 2,
    dadurch gekennzeichnet, dass die bewegliche Anordnung (50) eine Basis (60) umfasst, die mit dem Griff (55) zusammenwirkt, wobei der Griff (55) mit der Basis (60) durch eine Schwenkverbindung (62) verbunden ist, die dem Griff (55) einen Rotationsfreiheitsgrad in Bezug auf die Basis (60) und um den Stiel herum gibt, wobei die Basis (60) am Stiel (41) durch eine Gleitschienenverbindung (65) befestigt ist, wobei die Basis (60) nur in Bezug auf den Stiel (41) translatorisch beweglich ist, wobei der Griff (55) in Bezug auf die Basis (60) drehbar beweglich und in Translation mit der Basis (60) fest verbunden ist, und wobei die mechanische Bewegungsübertragung (36) an der Basis (60) befestigt ist.
  4. Steuerorgan nach einem der Ansprüche 1 bis 3,
    dadurch gekennzeichnet, dass die bewegliche Anordnung (50) ein Steuerstellglied (14) steuert, das eine Verschiebung der beweglichen Anordnung (50) über eine Steueramplitude erfordert, um einen gesamten Betriebsbereich des Steuerstellglieds (14) abzudecken, wobei sich die bewegliche Anordnung (50) außer Betrieb in einer zentrierten Position (POSO) zwischen einem ersten Anschlag (201) und einem zweiten Anschlag (202) befindet, und dass der erste Anschlag (201) und der zweite Anschlag (202) von der beweglichen Anordnung (50) aus der zentrierten Position (POSO) heraus nach einer der Steueramplitude entsprechenden Translationsbewegung der beweglichen Anordnung erreicht werden.
  5. Steuerorgan nach einem der Ansprüche 1 bis 4,
    dadurch gekennzeichnet, dass sich der Stiel (41) in Längsrichtung von einem proximalen Ende (42) zu einem freien Ende (43) erstreckt, wobei das proximale Ende (42) mit einem Gelenk (70) versehen ist, das dem Stiel einen Rotationsfreiheitsgrad um eine Drehachse (AX2) verleiht, und die erste Bewegungsrichtung (101) von dem proximalen Ende (42) zu dem freien Ende (43) verläuft.
  6. Steuerorgan nach einem der Ansprüche 1 bis 5,
    dadurch gekennzeichnet, dass sich der Stiel (41) in Längsrichtung von einem proximalen Ende (42) zu einem freien Ende (43) erstreckt, wobei das proximale Ende (42) mit einem Gelenk versehen ist, das dem Stiel einen Rotationsfreiheitsgrad um eine Drehachse (AX2) verleiht, dass der Griff (55) zwischen dem proximalen Ende (42) und dem freien Ende (43) angeordnet ist, und der Griff (55) unabhängig vom Stiel (41) ist, so dass eine Drehung des Stiels (41) um seine Drehachse (AX2) keine Verschiebung des Griffs (55) entlang des Stiels (41) induziert.
  7. Luftfahrzeug (1), das mit mindestens einem einen Schub ausübenden Antriebssystem (10) ausgestattet ist, wobei der Schub durch mindestens ein Steuerstellglied (14) geregelt ist, und das Steuerungsstellglied (14) durch eine Bewegungsübertragungskette (20) gesteuert ist, die zu dem Steuerstellglied (14) führt,
    dadurch gekennzeichnet, dass das Luftfahrzeug (1) mindestens ein Steuerorgan (40) nach einem der Ansprüche 1 bis 6 aufweist, das Steuerorgan (40) mechanisch mit der Bewegungsübertragungskette (20) verbunden ist und vorgesehen ist, um die Bewegungsübertragungskette (20) zu bewegen.
  8. Luftfahrzeug nach Anspruch 7,
    dadurch gekennzeichnet, dass die Bewegungsübertragungskette (20) mindestens ein Steuerungsstellglied (17) umfasst, wobei das Steuerungsstellglied (17) über eine von einem Piloten bedienbare Avionik-Steuerschnittstelle (18) gesteuert ist.
  9. Luftfahrzeug nach einem der Ansprüche 7 bis 8,
    dadurch gekennzeichnet, dass das Luftfahrzeug (1) zwei Antriebssysteme (10) mit Propellern (11, 12) umfasst, wobei der von jedem Propeller (11, 12) eines Antriebssystems ausgeübte Schub durch Modifizieren einer Blattneigung (13) dieses Propellers gesteuert wird, wobei das Luftfahrzeug (1) ein von einem Piloten betätigbares Steuersystem (16) aufweist, um die von den beiden Propellern ausgeübten Schübe auf unterschiedliche Weise zu modifizieren, wobei das Steuerorgan (40) es ermöglicht, die von den beiden Propellern ausgeübten Schübe auf die gleiche Weise zu modifizieren, die Bewegungsübertragungskette (20) mindestens einen Kombinator (22) umfasst, der mit dem Steuerorgan (40) und dem Steuersystem (16) sowie mit den beiden Propellern (11, 12) verbunden ist, und der Kombinator (22) eine von dem Steuerorgan (40) erzeugte Verschiebung und eine von dem Steuersystem (16) erzeugte Verschiebung mechanisch kombiniert.
  10. Luftfahrzeug nach einem der Ansprüche 7 bis 9,
    dadurch gekennzeichnet, dass das Steuerorgan (40) eine mechanische Bewegungsübertragung (36) umfasst, die an der beweglichen Anordnung (50) befestigt ist, ein Hebel (31) einerseits an der mechanischen Bewegungsübertragung (36) und andererseits an der Bewegungsübertragungskette (20) angelenkt ist, und der Hebel (31) um eine Scharnierachse (AX1) drehbar beweglich ist.
  11. Luftfahrzeug nach Anspruch 10,
    dadurch gekennzeichnet, dass das Luftfahrzeug (1) eine Mehrzahl von Steuerorganen (40) aufweist, die jeweils eine mechanische Bewegungsübertragung (36) umfassen, die mit der beweglichen Anordnung (50) des zugehörigen Steuerorgans verbunden ist, und dass jede mechanische Bewegungsübertragung (36) an den Hebel (31) angelenkt ist.
  12. Luftfahrzeug nach einem der Ansprüche 10 bis 11,
    dadurch gekennzeichnet, dass sich die Scharnierachse (AX1) zwischen zwei Endzonen (32, 33) des Hebels (31) erstreckt, und dass die mechanische Bewegungsübertragung (36) und die Bewegungsübertragungskette (20) an den Hebel (31) zwischen der Gelenkachse (AX1) und der gleichen Endzone (33) angelenkt sind.
  13. Luftfahrzeug nach einem der Ansprüche 10 bis 12,
    dadurch gekennzeichnet, dass das Luftfahrzeug (1) ein von einem Piloten betätigbares Immobilisierungssystem (37) aufweist, um den Hebel (31) im Normalbetrieb zu immobilisieren.
  14. Luftfahrzeug nach Anspruch 13,
    dadurch gekennzeichnet, dass das Immobilisierungssystem (37) mit einem mechanischen System versehen ist, das einen translatierbaren Sperrfinger (38) und eine Öffnung (39) des Hebels (31) beinhaltet, wobei der Sperrfinger (38) im Normalbetrieb in die Öffnung (39) eingreift, um eine Drehung des Hebels (31) zu verhindern, und im Handbetrieb von der Öffnung (39) gelöst ist, um eine Drehung des Hebels (31) zu ermöglichen.
  15. Verfahren zum Steuern eines Antriebssystems (10) eines Flugzeugs (1) nach einem der Ansprüche 7 bis 14,
    dadurch gekennzeichnet, dass der Griff (55) in einer ersten Drehrichtung (103) gedreht wird, um ihn entlang des Griffs (41) in der ersten Translationsrichtung (101) zu translatieren, um den durch das Antriebssystem (10) ausgeübten Schub zu erhöhen, und der Griff (55) in eine zweite Drehrichtung (104) gedreht wird, um ihn entlang des Griffs in die zweite Translationsrichtung (102) zu bewegen, um den durch das Antriebssystem (10) ausgeübten Schub zu verringern.
  16. Verfahren nach Anspruch 15,
    dadurch gekennzeichnet, dass das Luftfahrzeug (1) einen Indikator (80) mit einer Skala (81), die Schubwerte darstellt, und einem Zeiger (83) aufweist, der auf dieser Skala einen Wert eines aktuellen Schubs anzeigt, wobei die Nadel (83) bei zunehmendem Schub eine Drehung in einer ersten Bewegungsrichtung (105) und bei abnehmendem Schub in einer zweiten Bewegungsrichtung (106) ausführt, wobei die erste Drehrichtung (103) identisch mit der ersten Bewegungsrichtung (105) ist, und die zweite Drehrichtung (104) identisch mit der zweiten Bewegungsrichtung (106) ist.
EP17200291.7A 2016-11-30 2017-11-07 Steuerorgan, drehflügelflugzeug und verfahren Active EP3330177B1 (de)

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CN109625247A (zh) * 2018-11-30 2019-04-16 中国航空工业集团公司沈阳飞机设计研究所 一种可调节飞机侧杆臂托
FR3093077B1 (fr) * 2019-02-27 2021-01-22 Airbus Helicopters dispositif de renvoi assisté et aéronef
EP4361029A1 (de) * 2022-10-27 2024-05-01 Lockheed Martin Corporation Klappsteuerknüppel und verriegelungsmechanismus

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FR3059297A1 (fr) 2018-06-01
EP3330177A1 (de) 2018-06-06
KR101977153B1 (ko) 2019-05-10
CN108116674B (zh) 2020-12-29
CN108116674A (zh) 2018-06-05
US20180148167A1 (en) 2018-05-31
US10737775B2 (en) 2020-08-11
KR20180062430A (ko) 2018-06-08
FR3059297B1 (fr) 2018-11-09

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